Journal of the Korean Society for Aeronautical & Space Sciences (한국항공우주학회지)

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Boundary Layer Correction of Hypersonic Wind-tunnel Nozzle Designed by the Methods of Characteristics

특성곡선 해법 설계 극초음속 노즐의 경계층 보정

  • Received : 2014.08.19
  • Accepted : 2014.11.24
  • Published : 2014.12.01
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Abstract

A design procedure is established for hypersonic nozzles by using MOC(Method of Characteristics) and CFD. The inviscid nozzle contour is designed by MOC, then BLC(Boundary Layer Correction) is made by evaluating the boundary layer thickness from viscous CFD analysis. By comparing various definitions of the boundary layer thicknesses, it seems that the boundary layer thickness of 95% speed of the maximum value at the cross section satisfies best the design Mach number. Design procedure is as follow; MOC design, grid generation, inviscid analysis, viscous analysis, BLC and viscous analysis for confirmation and post-processing. All procedures are made automatically by using the batch processing.

연구에서는 MOC 및 CFD를 이용한 극초음속 노즐 설계 절차를 수립하였다. MOC를 이용하여 설계된 비점성 노즐 형상에 대하여, 점성 유체 전산 해석을 통하여 경계층 두께를 산출하여 노즐 형상을 보정하였다. 여러 가지의 경계층 두께 정의를 비교한 결과, 노즐 단면 최대 속력의 95% 속력을 가지는 경계층 두께의 정의가 설계 마하수를 가장 잘 만족하는 것으로 여겨진다. 노즐 설계과정은 MOC 설계에 대한 격자 형성, 비점성 해석 및 점성 해석, 경계층 보정 및 점성 해석에 의한 확인 및 결과 도출의 순서로 진행되며, 모든 과정은 자동 일괄 처리토록 작성되었다.

Keywords

References

  1. Sivells, J.C., "A Computer Program for the Aerodynamic Design of Axisymmetric and Planar Nozzles for Supersonic and Hypersonic Wind Tunnels," AEDC-TR-78-63, 1978
  2. Sivells, J.C, "Aerodynamic Design of Axisymmetric Hypersonic Wind Tunnel Nozzles," AIAA 4th Aerodynamic Testing Conference, Cincinnati, Ohio, 28-30 April, 1960
  3. Shope, F.L., "Contour Design Techniques for Super/Hypersonic Wind Tunnel Nozzles," AIAA 2006-3665, 24th AIAA Applied Aerodynamics Conference, San Fransisco, California, 5-8 June, 2006
  4. Sauer, R., "General Characteristics of the Flow Through Nozzles at Near Critical Speeds," National Advisory Committee for Aeronautics, Technical Memorandum, No.1147, 1947.
  5. Korte, J.J., "Inviscid Design of Hypersoninc Wind Tunnel Nozzles for a Real Gas," AIAA-2000-0677, 38th Aerospace Sciences Meeting & Exhibit, Reno, NV, 10-13 January, 2000.
  6. Charles B. Johnson, Lillian R. Boney, James C. Ellison, Wayne D. Erickson, "Real-Gas Effects on Hypersonic Nozzle Contours with a Method of Calculation", NASA TN D-1622, 1963.
  7. Plyashechnik, V.I., Byrkin, A.P., Verkhovsky, V.P., "Gasdynamic Design of Shaped Nozzles for Supersoninc Wind Tunnels, Allowing for Viscosity," West-East High Speed Flow Field Conference, Moscow, Russia, Nov. 19-22, 2007
  8. Gordon, S., McBride, B.J., "Computer program for Calculation of Complex Chemical equilibrium Compositions and Applications," NASA RP-1411, Part I, 1994.
  9. Won, S.-H., Jeung, I.-S. and Choi, J.-Y., "Verification and Validation of the Numerical Simulation of Transverse Injection Jets using Grid Convergence Index," Journal of KSAS, Vol.34, No.4, pp.53-62, Apr. 2006. https://doi.org/10.5139/JKSAS.2006.34.4.053
  10. White, F.M., Fluid Mechanics, 6th ed., McGraw-Hill, 2007, Chaps. 7, pp.482-488